CN1907806A - helicopter with tilted front rotary wing - Google Patents
helicopter with tilted front rotary wing Download PDFInfo
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- CN1907806A CN1907806A CNA2005100873761A CN200510087376A CN1907806A CN 1907806 A CN1907806 A CN 1907806A CN A2005100873761 A CNA2005100873761 A CN A2005100873761A CN 200510087376 A CN200510087376 A CN 200510087376A CN 1907806 A CN1907806 A CN 1907806A
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- helicopter
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to an improved front-rotor swivel vertical take-off plane, wherein the front wing 11 with front rotor 26 is arranged at the front part of frame 1; the main wing 78 is under the back rotor 98 at the back of frame; said structure can make the area of disk of back rotor larger than two front rotors 26, and make the area ratio between the front wing and the main wing is same as the boost ratio generated by the front and back rotors; therefore, the front wing can share the same boost generated by the front rotor, when plane takes off, to reduce the boost pressure loaded by the main wing, to improve the forward flying efficiency.
Description
The present invention relates to a kind of omniplane, particularly helicopter with tilted front rotary wing.
In application number was 03137211.2 application for a patent for invention book, the main wing of the helicopter with tilted front rotary wing of being introduced had been located at the position between preceding rotor and the back rotor.This position arrangement of main wing requires two preceding rotors and the lift that the back rotor is produced can not differ bigger, as the lift that allows the back rotor be produced is bigger, just the position of main wing is not easy to adapt to the variation that moves after the airplane ascensional force center of gravity.In addition, when horizontal flight, because of aircraft weight is carried by the main wing of medium position substantially, the ability of bearing preceding rotor lift load that front wing had when taking off vertically just is not utilized, thereby has caused the corresponding structure waste because of function is idle.
The purpose of this invention is to provide a kind of improved helicopter with tilted front rotary wing, its topology layout is not only more reasonable, but also helps obtaining higher flight efficiency.
Helicopter with tilted front rotary wing of the present invention has the fuselage that adopts wheel undercarriage, position on forebody leans on is provided with front wing, by vert cabin and preceding rotor shaft preceding rotor is housed respectively at the front wing two ends, cross moving axis between the two preceding rotor shaft in preceding rotor is in transmission connection, be provided with rotor behind the coaxial reverse on the boss on fuselage afterbody, every secondary back rotor is made of two blades, during back rotor stall, blade is parked in and fuselage line of centers positions aligning place, the rotor shaft of back rotor through which is provided with power-transfer clutch tween drive spindle and the cross moving axis of preceding rotor be in transmission connection, on fuselage, also be provided with main wing; The rotor disk area of back rotor is than the rotor disk area greater than two preceding rotors, the rotor shaft lower position place of rotor after main wing is arranged on substantially, front wing is corresponding with the ratio of the lift greatly of back rotor generation with the less lift that two preceding rotors produce basically with the ratio of the area size of main wing.
To in further the improving of structure of the present invention, be provided with at the rear side of main wing and still have a flap under the larger area of wing flap function, between main wing and following flap, the return oil cylinder is installed, following flap is rolled under can be corresponding in gas washing stream down.Part beyond the following flap of main wing is made into the outer wing that verts that is equipped with by tiliting axis, and both can vert synchronously in the vert cabin of this outer wing on transmission controlling mechanism and front wing, also can carry out independent angle and control.In addition, be respectively equipped with vertical tail on the main wing of every side or the outer wing that verts, when vertical tail was located on the outer wing that verts, after the outer wing that verts forwarded the upright position to by level, the yaw rudder on the vertical tail still can be diverted manipulation.
The back rotor of helicopter with tilted front rotary wing can be effectively controlled among the present invention in order to make, on the rotor shaft of back rotor, be respectively equipped with chuck, flower wheel and brake disc (or brake hubs), on the periphery (perhaps upper and lower sides end face) of chuck, be provided with the double inclined plane draw-in groove of one or two symmetric arrangement, on the pivot shaft of boss, be equipped with and be subjected to the location pressure arm that oil cylinder is controlled, its head has pinch roller; Drive wheel and the free-wheel clutch of flower wheel on the rotor shaft through being in transmission connection driven by the axle drive shaft of driven at low speed device; After back rotor is braked stall by brake disc, the rotor shaft of driven at low speed device rotor after free-wheel clutch drives slowly runs, when oil cylinder makes the pinch roller of location on the pressure arm be pressed in the draw-in groove on the chuck that forwards to, the stall of driven at low speed device, the blade of corresponding back rotor also forwards to and fuselage line of centers positions aligning place.In addition, also can allow the location pressure arm be hinged on the pivot shaft of boss through hydraulic pressure or spring centering sleeve.
Rotor verts in the mounting means of cabin before of the present invention, vert the cabin by bearing installation on the support sleeve of front wing outboard structure, in outboard structure, be provided with bearing and Transmission Room, the cross moving axis of rotor passes on the bearing that reaches behind bearing, Transmission Room and the support sleeve in the cabin of verting before driving, the displacement control cover that is enclosed within on the cross moving axis is housed in support sleeve, this control cover displacement flower wheel inner and in the Transmission Room links to each other, the other end puts in the cabin of verting, and is in transmission connection through the displacement arm of power wheel and pitch-changing mechanism and preceding each blade of rotor.
Be control the verting of cabin of verting, on the support sleeve of salient under inboard basifacial shaft in the cabin of verting and the front wing ala lateralis, the actuator of verting is housed, the bearing seat of this actuator in its front shell is installed on the support sleeve, be provided with driven wheel passing the axle drive shaft outer end that support sleeve enters in the housing, the bevel gear that the driven gear that is meshed with it is connected as a single entity through its inboard drives the driven bevel pinion on the screw rod of bearing seat back, screw is on the bearing of the bearing at housing rear portion and rear side connecting cylinder back seat, and by the driven bevel pinion of its front end and the back-up ring axial limiting of rear end, stretch out two parallel expansion links from the nut start plate that is contained on the screw rod, the slide opening that two expansion links pass front shell top chock both sides fuses with the connector that has bearing hole, and the actuator of verting links to each other with a shaft on the cabin of verting through the connector of its front end.
When the expansion link of the actuator of verting was in retrieving position, the support sleeve under a shaft in the cabin of verting and the wing on the salient was on the same level attitude substantially.
In the engine installation of helicopter with tilted front rotary wing of the present invention is arranged, the piston of rotor or the front or rear portion that turboshaft engine is located at fuselage before driving, drive power-transfer clutch fwd leading portion tween drive spindle by transmission gear, the turboshaft engine that drives the back rotor is located at fuselage afterbody, drives the back segment tween drive spindle of power-transfer clutch back by transmission gear.
After the present invention adopts improved helicopter with tilted front rotary wing, since main wing be located at basically the back rotor rotor shaft below, when determining the blade area size of front wing and main wing, just can decide according to the lift size that rotors before two and back rotor are produced when the vertical takeoff and landing (VTOL), the lift that rotor produces before two is less, and the blade area of front wing is also wanted corresponding minimizing.The lift of back rotor is bigger, and area of main wing also should be bigger below it.The front wing of determining according to this mode and main wing are put down when flying at aircraft, front wing can produce the lift identical with preceding rotor (during vertical takeoff and landing (VTOL)), eliminated this deficiency that does not need front wing generation lift before improving, the lift that also allows main wing bear is corresponding to be reduced, and makes the structure of aircraft and lifting force of wings distribution more reasonable.
Because to compare with general propeller aeroplane than the preceding rotor of minor diameter also is bigger, still can produces and fly application force before enough.Therefore, when adopting the back rotor of relative larger diameter, not only can allow this omniplane have bigger vertical upward force, carrying capacity is increased.And when horizontal flight, because of the engine power of rotor after driving is bigger, after back rotor stall is closed, fuel oil is saved in a large number, drive the running for more time of preceding rotor with this part fuel oil of being saved by driving engine, just can increase considerably the flying distance of aircraft.
In specific implementation process of the present invention, rotor and back rotor have the suitable diameter that varies in size before not only will making, and also will allow both have different disk loadings.The disk loading of preceding rotor is greater, to help reaching forward flight speed and the higher efficient of cruising faster, makes its flat state that flies close with the ordinary fixed wing aircraft.The disk loading of back rotor reduces relatively than preceding rotor, is not very big so that this aircraft on average descends gas washing stream when vertical takeoff and landing (VTOL), approaches general helicopter.
This omniplane of the present invention is in the process of hovering, because of changing lift stool and urine and can allow aircraft moves ahead, sidesway and retreating to the left and right by adjusting before two the pitch of rotors and back rotor, make it be in different following folding deflection angles and yaw rudder of changing on the vertical tail just can be realized the tune of aircraft forward and the swing at rear portion respectively and handle two outer wings that vert, make the forward and backward rotor of this omniplane adopt simple propeller hub structure get final product, needn't resemble the propeller hub structure that adopts complexity the helicopter with displacement function.
Because helicopter with tilted front rotary wing of the present invention has the bigger load that takes off vertically, flying speed is very fast simultaneously, flying distance is far away, in the reality so long as not being used for the special operation of hovering, all alternative existing pure helicopter.But vertical takeoff and landing (VTOL), the fast voyage of speed overall merit far away also makes this omniplane can carry out the task that a lot of fixed wing aircrafts are difficult to finish, thereby can further enlarge the field of application of this omniplane of the present invention again.
The present invention is further detailed explanation below in conjunction with the drawings and specific embodiments.
Fig. 1 is the birds-eye view of the large-scale omniplane of the present invention.
Fig. 2 is the lateral plan of omniplane among Fig. 1.
Fig. 3 is the front elevation of omniplane among Fig. 1.
Fig. 4 is the structure cutaway view of flap under main wing and the rear side thereof in the omniplane of the present invention.
Fig. 5 is the structural representation of back of the present invention rotor brake, driven at low speed device and location pressure arm
Fig. 6 is the location pressure arm structural representation of band centring sleeve tube among the present invention.
Fig. 7 is the vert structure cutaway view in cabin of omniplane of the present invention.
The cabin of verting among Fig. 8 is in horizontality, and preceding rotor forwards the front wing front to.
The cabin of verting among Fig. 9 is in plumbness, preceding rotor forward to main wing above.
Figure 10 is the vertical view cutaway drawing of actuator of verting among the present invention.
Figure 11 is the side view cutaway drawing of actuator of verting among Figure 10.
Figure 12 is the birds-eye view of small-sized omniplane of the present invention.
Figure 13 is the lateral plan of the middle-size and small-size omniplane of Figure 12.
Figure 14 is the engine drive system arrangement plan of the forward and backward rotor of small-sized omniplane of the present invention.
What Fig. 1, Fig. 2 and Fig. 3 provided is the three-view diagram of the large-scale helicopter with tilted front rotary wing of the present invention.It has the fuselage 1 that adopts wheel undercarriage, on fuselage, be provided with front wing 11 and main wing 78, front wing is located at the front portion of fuselage 1 and locates on the top, rotor 26 before be equipped with respectively by vert cabin 31 and preceding rotor shaft 29 at the front wing two ends, cross moving axis 23 between the two preceding rotor shaft 29 in front wing is in transmission connection, so that rotor run-in synchronisms before two.Back rotor 98 is located on the boss 4 above the fuselage afterbody, two secondary back rotors of coaxial reverse are cancelled out each other its existing out-of-balance force when rotating, the every secondary back rotor that is made of two blades is when stall, can be parked in the minimum drag position of aliging with fuselage line of centers 10, suffered resistance is less in that aircraft is flat when flying to allow the back rotor.Main wing 78 is positioned at the rear portion of fuselage 1, is located at the rotor shaft 106 lower position places of back rotor 98 substantially.In omniplane of the present invention, when vertical takeoff and landing (VTOL), because of front wing 11 be in before rotor 26 below, behind rotor 98 lower positions, front wing 11 is corresponding with the ratio of the lift greatly of back rotor 98 generations with the less lift of two preceding rotors 26 generations basically with the ratio of the area size of main wing 78 after main wing 78 is located at.
Before determining, when the diameter separately of rotor and back rotor and lift size, also be bigger owing to compare with general propeller aeroplane than the preceding rotor of minor diameter, before still allowing the rotor generation enough before fly application force.Therefore, the rotor disk area of rotor 98 is greater than the rotor disk area of two preceding rotors 26 after will allowing in the reality, and the lift that rotor is produced after allowing is also than the lift (during vertical takeoff and landing (VTOL)) that is produced greater than two preceding rotors.The lift size is not only relevant with rotor disk area, also relevant with determined disk loading size, fly efficient and allow aircraft reach flying speed faster before higher for rotor before helping making has, the disk loading of rotor is bigger before should allowing, then the disk loading of rotor will correspondingly be lower than preceding rotor, is not very big so that make the average stream of gas washing down of aircraft in floating state.After diameter that should have according to forward and backward rotor and disk loading size are determined corresponding forward and backward rotor lift size, just front wing 11 should produce in the time of can determining flat flying the less lift (when hovering) identical with preceding rotor 26, corresponding before blade area also less; Main wing 78 should produce when also determining flat flying the big lift (when hovering) identical with back rotor 98, corresponding area of plane is also bigger, shown in Fig. 1 birds-eye view.Generally speaking, the lift that rotors are produced before two can be defined as being equivalent to the lift of rotor behind the 2/3-1/4, the area of front wing and main wing also should be determined according to the lift size of forward and backward rotor, also will consider the center of gravity leading that helps the aircraft smooth flight in concrete enforcement.
Though it is less that front wing 11 is compared main wing 78 areas, when fuselage 1 and the preceding blade area between the cabin 31 of verting are not enough, as shown in Figure 1, can be before 31 outsides, cabin of verting be set up outer wing 53.
Since main wing 78 be located at the back rotor 98 below, main wing produces big resistance in the following gas washing stream of back rotor when avoiding vertical takeoff and landing (VTOL), as shown in fig. 1, rear side at main wing is provided with flap 86 under the larger area, following flap 86 is installed as shown in Figure 4 in the structure of main wing rear side, the return oil cylinder 91 that is equipped with between main wing 78 and following flap 86, this oil cylinder make down flap at the flat retrieving position that is in when flying of aircraft.And during the aircraft vertical takeoff and landing (VTOL), the pressure oil of sever supply return oil cylinder 91, following flap is corresponding folding down under the following gas washing stream effect of back rotor just, as shown in phantom in FIG., to reduce the air-flow resistance that main wing was produced, return oil cylinder at this moment also can impact the swing that following flap is produced in air-flow and carry out damping.Flap has occupied the flap configuration of former wing rear side under the cause, as also playing enough wing flap effects by the downward angular deflection of controlling down flap in-flight, can still allow down flap substitute the wing flap of home position.As have only the retrusive of employing wing flap just can reach due control action, can set up retrusive wing flap (drawing among the figure) at following flap rear side.Equally, for reduce the resistance that main wing 78 is produced in following gas washing stream, part is made into the outer wing 94 that verts that is equipped with by tiliting axis 81 beyond the following flap 86 of main wing, both can vert synchronously in the vert cabin 31 of this outer wing on transmission controlling mechanism and front wing 11, also can be to finish to hover attitude accordingly and carry out the control of independent angle.As in gas washing flows down, allowing the outer wing 94 that the verts ' while deflection forward or backward that forwards the upright position to, just can allow the omniplane in hovering move forward or backward.As control the outer wing 94 that verts of both sides ' to opposite angle position deflection, just can allow forebody swing to controlled direction.
When under the following gas washing stream effect of back rotor, jitter phenomenon taking place as main wing 78 in the reality, can between main wing and fuselage, establish and tiltedly draw strength beam, to strengthen the structural strength of main wing.
In the different flight state of helicopter with tilted front rotary wing, when aircraft carries out vertical takeoff and landing (VTOL), forward 26 on the preceding rotor 26 to ' shown in position (referring to Fig. 2 and Fig. 3), with the back rotor 98 common lift upwards that produce of rotation.In this state, the following flap on the main wing 78 forwards 86 for 86 times to ' the position, the outer wing 94 that verts in the main wing outside also forwards 94 to ' the position, drawn as dotted line among Fig. 3.When aircraft is finished when flying state before the process of taking off vertically need change over to, preceding rotor tilts forward gradually from 26 ' position, the component that generation is sent as an envoy to and flown before the aircraft, fly before allowing aircraft begin, in this course, the front wing 11 of aircraft and main wing 78 also begin to produce corresponding lift, cooperate 98 corresponding angles of attack that reduce blade of back rotor of running, reduce the raising force of its generation gradually.When current rotor 26 forwards forward position fully to, all application forces that preceding rotor produces all are used for aircraft is flown forward, aircraft has also reached certain forward flight speed, the weight of aircraft just changes by front wing 11 and main wing 78 carries respectively, the following flap 86 and the outer wing 94 that verts on the main wing are also got back to straight position, and 99 of the rotor blades in corresponding back are adjusted to the zero lift angle.If aircraft changes over to long apart from cruising condition, the turbine engine that drives the back rotor just is closed, allow the back rotor stop operating, and the minimum drag position that its blade is parked in align with fuselage line of centers 10, with the consumption of direct reduction fuel, reduce back rotor resistance, thereby increase substantially the efficient of cruising of aircraft.
Stopping by the turbine engine drive, to being fixed on fuselage line of centers positions aligning from the back rotor is to realize like this, after aircraft entered the state of normaling cruise, the turbine engine that drives the back rotor shuts down, the brake disc 118 of the back rotor that rotates under effect of inertia on rotor shaft 106 acted on by brake gear 119 and stopping operating.After the back rotor stall, the axle drive shaft 116 of driven at low speed device 117 on it, free-wheel clutch 115, the flower wheel 112 that drive wheel 114 and driving band 113 drive on the rotor shaft 106 slowly runs, simultaneously, control oil cylinder 130 is also made location pressure arm 120 press to chuck 108 on the rotor shaft 106 through the pinch roller on it 121 by the pressure oil effect, when the pinch roller 121 when the location on the pressure arm is pressed in the draw-in groove 110 on the chuck 108 that forwards to, back rotor is tightened stall by pinch roller, also corresponding the stopping of driven at low speed device 117 drives, and at this moment corresponding back rotor blade 99 is just forwarding the minimum drag position (referring to Fig. 1) of aliging with fuselage line of centers 10 to.In state shown in Figure 5, draw-in groove 110 on the chuck 108 is stuck along the position that direction shown in the arrow 111 will forward pinch roller 121 to, jammed chuck offset some small amount still under the low effect of inertia of blade, inclined-plane by draw-in groove 110 makes pinch roller 121 corresponding resiliences, and the pressure of oil cylinder 130 is subdued the inertia of blade and is pushed back the chucking position by pinch roller 121, the blade of back rotor after more and more littler so several times swing, is finally located (referring to chuck position among Fig. 6) by the pinch roller chucking together with its chuck.In the axle sleeve of rotor shaft 106 axle 102 in the rotor of another secondary back rotor of upper strata, the identical switched in opposite of both rotating speeds, two secondary rotor blades after the stall all are positioned in and fuselage line of centers positions aligning place.
The location pressure arm 120 that Fig. 6 provides is on hydraulic pressure centring sleeve tube 129 is hinged on pivot shaft 128 in the boss, after adopting this structure, just be pressed into pinch roller 121 in the draw-in groove on the chuck 108 110 with no longer resilience, the low-inertia force of back rotor blade is subdued by hydraulic pressure centring sleeve tube 129.In concrete enforcement, also available brute spring replaces hydraulic coupling to make spring loaded centring sleeve tube.Being provided with the draw-in groove 110 of two symmetries on the chuck 108 among Fig. 5 and Fig. 6, be the snap action power of increase location pressure arm, but also two of relative set is located pressure arm 120.
In omniplane of the present invention, preceding rotor 26 is contained in the outer end of front wing 11 by the cabin 31 of verting, and is relatively large because of the diameter of preceding rotor in big-and-middle-sized aircraft, and rotor is driven by the turboshaft engine that is located in the cabin of verting before can allowing.Because by locking, its rotor shaft 106 is the cross moving axis 23 of rotor before the tween drive spindle 5 and two of band power-transfer clutch 8 be in transmission connection (referring to Fig. 1) to the back rotor when flying before aircraft.Back rotor is driven by the turbine engine that is located at fuselage afterbody, and its power is delivered to the back segment tween drive spindle 9 of power-transfer clutch 8 back through transmission gear, drives back rotor 98 by this beam warp bevel gear and retarder again.And in middle-size and small-size aircraft, because of the diameter of preceding rotor also diminishes relatively, can drive by the driving engine that is located in the fuselage 1.
Before employing allows rotor by the engine driving mode in the fuselage after, rotor verts cabin structure as shown in Figure 7 before installing, the cabin 31 of verting of preceding rotor 26 is installed on the support sleeve 14 of front wing outboard structure 12 by the bearing 36 on its structure shell 32, in outboard structure 12, be provided with bearing 21 and Transmission Room 13, the cross moving axis 23 of rotor 26 passes bearing 21 before driving, reach behind Transmission Room 13 and the support sleeve 14 on the bearing 38 in the cabin structure shell 32 that verts, in the outer end of cross moving axis 23 driven wheel 42 is housed, bevel gear 41 on the driven gear 43 of this gear through being meshed and the minor axises 37 in the middle of the bevel gear that links to each other 40 drives, allow cross moving axis 23 realize entering being in transmission connection of turnover 90 degree behind the cabin of verting, the front end of middle minor axis 37 again by planetary reduction gear group 39 drive be equipped with before the preceding rotor shaft 29 of rotor 26.
The displacement control cover 20 that is enclosed within on the cross moving axis 23 is housed in support sleeve 14, this control cover displacement flower wheel 19 inner and in the Transmission Room 13 links to each other, the other end stretches in the structure shell 32 in the cabin 31 of verting, displacement ring 50 on the expenditure axle sleeve 35 of the power wheel 18 of its end, screw rod rocking arm pitch-changing mechanism 49 and structure shell 32 front portions links to each other, and the displacement ring links to each other through the displacement arm 28 of pitch-change-link 51 with each blade 27 of preceding rotor respectively again.In the cabin structure that verts that Fig. 7 provides,, reserved the space that displacement control cover 20 is installed, thereby rotor is subjected to the control of failure-free displacement before allowing because of the cross moving axis 23 that passes support sleeve 14 does not contact with support sleeve.To the manipulation of displacement control cover 20, both can adopt the mode that drive link 17 drives displacement flower wheels 19 of pass through as shown in FIG., also can adopt by being located at the mode that interior hydraulic pressure of front wing outboard structure 12 or automatically controlled actuator directly drive displacement driving wheel 18.
For the control of verting in the cabin of verting, also provided the organization plan of the actuator of verting accordingly in the present invention.The installation site of the actuator of verting 54 such as Fig. 8 and shown in Figure 9, it is installed on the support sleeve 16 of salient 15 under vert cabin 31 inboard basifacial shafts 33 and the front wing ala lateralis.The actuator 54 of verting among Fig. 8 is in retracted state, at this moment verting, the support sleeve 16 of salient 15 is on the same level attitude substantially under shaft 33 and the wing in cabin 31, rotor 26 is transferred to the front of front wing 11 before corresponding with the cabin 31 of verting, the actuator 54 of verting in this state also forwards level attitude to, and on put below the fairing 25 in the front wing outside.The double-telescopic rod 74 of the actuator of verting among Fig. 9 54 is in the state that stretches out fully, the also corresponding bottom in its rear portion, the cabin 31 of verting at this moment is pushed to upright position upwards, allow preceding rotor on it forward to front wing 11 above, cooperate aircraft to carry out vertical takeoff and landing (VTOL).
The structure of the actuator of verting as shown in Figure 10 and Figure 11, the bearing seat 57 of the actuator of verting 54 in its front shell 55 is sleeved on the support sleeve 16 of salient 15 under the wing, be provided with driven wheel 60 passing the outer end that support sleeve enters the axle drive shaft 59 of housing 55, the bevel gear 62 that the driven gear 61 that is meshed with it is connected as a single entity through the inboard drives the driven bevel pinion 65 on the screw rod 66 of bearing seats 57 back.On the bearing 68 that screw rod 66 is contained in housing 55 rear portions and the bearing 71 of rear side connecting cylinder back seat 70, and by the driven bevel pinion 65 of its front end and back-up ring 67 axial limitings of rear end.Nut start plate 73 is housed on screw rod 66, stretches out the slide opening 56 that two parallel expansion link 74, two expansion links pass front shell 55 top chocks 57 both sides, fuse with the connector 75 that has bearing hole 76 from this start plate.The actuator of verting 54 links to each other with a shaft 33 on the cabin 31 of verting through the connector 75 of its front end.The given actuator of verting utilizes double-telescopic rod 74 to drive the cabin of verting among the figure, structurally can bear bigger stretching action power.Allow two expansion links stretch out, also reduced actuator along the thickness on axle drive shaft 59 directions from the bearing seat both sides in the housing.The screw rod 66 that drives two expansion links is that force way is comparatively reasonable by the form effect nut start plate 73 that bears pulling force.
In the reality, also can be used to the actuator of verting of this structure to control the outer wing 94 that verts of main wing 78 both sides, so that keep the synchronism of molar behaviors with the cabin 31 of verting of preceding rotor.
What Figure 12 and Figure 13 provided is the External view of the small-sized helicopter with tilted front rotary wing of the present invention, this blimp has 4～5 seats, because of inconvenience is located at tween drive spindle on the line of centers of fuselage, just its leading portion transmission shaft has been located in the structural frames 3 of fuselage passenger cabin 2 sides.
Figure 14 is the layout scheme drawing of the driving engine of helicopter with tilted front rotary wing in Figure 12 and 13 and tween drive spindle etc.In the engine position scheme that Figure 14 provides, for avoiding aircraft passenger compartment, the first half of tween drive spindle 5 has been located at the side of fuselage 1, and this rear end is in transmission connection through side transmission gear 138, leading portion tween drive spindle 7, power-transfer clutch 8, back segment tween drive spindle 9 and transmission gear 142 tween drive spindle 5 with the drive rotor shaft 106 of back.The piston engine 135 (also can be turboshaft engine) of rotor 26 has been located at the rear portion (perhaps being arranged in forebody) of fuselage 1 before driving, and drives power-transfer clutch 8 fwd leading portion tween drive spindles 7 by transmission gear 137.The turboshaft engine 139 that drives back rotor 98 is located at fuselage 1 rear portion, drives the back segment tween drive spindle 9 of power-transfer clutch 8 back by transmission gear 141.Two kinds of driving engines of piston type and whirlpool axle are set are in order to utilize the fuel-efficient characteristics of piston engine to carry out cruising flight, and in light weight, high-power turboshaft engine is mainly used to drive the back rotor and carries out vertical takeoff and landing (VTOL) by aircraft.Certainly, when piston engine broke down shutdown, turboshaft engine also can be used as the alternative engine place in operation, thereby increases the safety in utilization of this omniplane.
If a kind of like this driving engine can be installed, can send fully loaded power when the aircraft vertical takeoff and landing (VTOL) drives forward and backward rotor and turns round jointly, and when before cruising, flying, rotor rotation before only driving with about 1/3 power with the oil consumption of corresponding reduction again then can be provided with the turboshaft engine of rotor after second drive.
Claims (10)
1, a kind of helicopter with tilted front rotary wing, it has the fuselage (1) that adopts wheel undercarriage, position on forebody leans on is provided with front wing (11), by the cabin of verting (31) and preceding rotor shaft (29) preceding rotor (26) is housed respectively at the front wing two ends, cross moving axis (23) between the two preceding rotor shaft (29) in front wing is in transmission connection, rotor (98) after on the boss (4) of fuselage (1) above the rear portion, being provided with coaxial reverse, every secondary back rotor is made of two blades (99), during back rotor stall, blade is parked in and fuselage line of centers (10) positions aligning place, the tween drive spindle (5) of the rotor shaft (106) of back rotor (98) through which is provided with power-transfer clutch (8) is in transmission connection with the cross moving axis (23) of preceding rotor, on fuselage (1), also be provided with main wing (78), feature of the present invention is: the rotor disk area of back rotor (98) is than the rotor disk area greater than two preceding rotors (26), main wing (78) is located at rotor shaft (106) the lower position place of back rotor (98) substantially, and front wing (11) is corresponding with the ratio than big lift that back rotor (98) produces with the less lift that two preceding rotors (26) produce basically with the ratio of the area size of main wing (78).
2, according to the helicopter with tilted front rotary wing of claim 1, it is characterized in that: be provided with at the rear side of main wing (78) and still have a flap (86) under the larger area of wing flap function, between main wing and following flap return oil cylinder (91) is installed, following flap can correspondingly rolled over down in the gas washing stream down.
3, according to the helicopter with tilted front rotary wing of claim 2, it is characterized in that: the following flap (86) of main wing (78) part in addition is made into the outer wing that verts (94) that is equipped with by tiliting axis (81), both can vert synchronously in the vert cabin (31) of this outer wing on transmission controlling mechanism and front wing, also can carry out independent angle control.
4, according to the helicopter with tilted front rotary wing of claim 3, it is characterized in that: on the main wing (78) of every side or the outer wing that verts (94), be respectively equipped with vertical tail (96), when vertical tail is located on the outer wing that verts, after the outer wing that verts forwarded the upright position to by level, the yaw rudder on the vertical tail (97) still can be diverted manipulation.
5, according to claim 2,3 or 4 helicopter with tilted front rotary wing, it is characterized in that: the back rotor (98) rotor shaft (106) on be respectively equipped with chuck (108), from flower wheel (112) and brake disc (118) (or brake hubs), on the periphery (109) (perhaps upper and lower sides end face) of chuck (108), be provided with the double inclined plane draw-in groove (110) of one or two symmetric arrangement, on the pivot shaft (128) of boss, be equipped with and be subjected to the location pressure arm (120) that oil cylinder (130) is controlled, its head has pinch roller (121); Drive wheel (114) and the free-wheel clutch (115) of flower wheel (112) on the rotor shaft (106) through being in transmission connection driven by the axle drive shaft of driven at low speed device (117) (116); After back rotor is braked stall by brake disc (118), the rotor shaft (106) of driven at low speed device (117) rotor after free-wheel clutch (115) drives slowly runs, when oil cylinder (130) makes pinch roller (121) on location pressure arm (120) be pressed in the draw-in groove (110) on the chuck (108) that forwards to, the stall of driven at low speed device, corresponding back rotor blade (99) also forwards to and fuselage line of centers (10) positions aligning place.
6, according to the helicopter with tilted front rotary wing of claim 5, it is characterized in that: location pressure arm (120) is hinged on the pivot shaft (128) of boss through hydraulic pressure or spring centering sleeve (129).
7, helicopter with tilted front rotary wing according to claim 5, it is characterized in that: the cabin of verting (31) of preceding rotor by bearing installation on the support sleeve (14) of front wing outboard structure (12), in outboard structure, be provided with bearing (21) and Transmission Room (13), the cross moving axis (23) of rotor passes bearing (21) before driving, reach behind Transmission Room (13) and the support sleeve (14) on the bearing (38) in the cabin of verting (31), the displacement control cover (20) that is enclosed within on the cross moving axis (23) is housed in support sleeve (14), this control cover displacement flower wheel (19) inner and in the Transmission Room (13) links to each other, and the other end puts in the cabin of verting (31), displacement arm (28) through power wheel and pitch-changing mechanism and preceding each blade of rotor is in transmission connection.
8, helicopter with tilted front rotary wing according to claim 7, it is characterized in that: on the support sleeve (16) of salient (15) under the cabin of verting (31) inboard basifacial shafts (33) and the front wing ala lateralis, the actuator of verting (54) is housed, the bearing seat (57) of this actuator in its front shell (55) is installed on the support sleeve (16), be provided with driven wheel (60) passing axle drive shaft (59) outer end that support sleeve enters in the housing (55), driven bevel pinion (65) on the screw rod (66) of bevel gear (62) drive bearing seat (57) back that the driven gear that is meshed with it (61) is connected as a single entity through the inboard, on the bearing (68) that screw rod (66) is contained in the housing rear portion and the bearing (71) of rear side connecting cylinder back seat (70), and by the driven bevel pinion (65) of its front end and back-up ring (67) axial limiting of rear end, stretch out two parallel expansion links (74) from the nut start plate (73) that is contained on the screw rod (66), two expansion links pass the slide opening (56) of front shell (55) top chock (57) both sides, fuse with the connector that has bearing hole (76) (75), the actuator of verting (54) links to each other with a shaft (33) on the cabin of verting (31) through the connector (75) of its front end.
9, helicopter with tilted front rotary wing according to Claim 8, it is characterized in that: the expansion link (74) of the actuator of verting (54) is when being in retrieving position, and the support sleeve (16) under a shaft (33) of the cabin of verting (31) and the wing on the salient (15) is on the same level attitude substantially.
10, according to the helicopter with tilted front rotary wing of claim 5, it is characterized in that: the piston of rotor or the front or rear portion that turboshaft engine (135) is located at fuselage (1) before driving, drive power-transfer clutch (8) fwd leading portion tween drive spindle (7) by transmission gear (137), the turboshaft engine (139) that drives the back rotor is located at fuselage (1) rear portion, drives the back segment tween drive spindle (9) of power-transfer clutch (8) back by transmission gear (141).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2005100873761A CN1907806A (en) | 2005-08-02 | 2005-08-02 | helicopter with tilted front rotary wing |
| PCT/CN2006/001944 WO2007014531A1 (en) | 2005-08-02 | 2006-08-02 | A vtol aircraft with tilt front rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2005100873761A CN1907806A (en) | 2005-08-02 | 2005-08-02 | helicopter with tilted front rotary wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1907806A true CN1907806A (en) | 2007-02-07 |
Family
ID=37699072
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2005100873761A Pending CN1907806A (en) | 2005-08-02 | 2005-08-02 | helicopter with tilted front rotary wing |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN1907806A (en) |
| WO (1) | WO2007014531A1 (en) |
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